SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-28-140, PA-28-150, PA-28-160, PA-28-180, PA-28-235, PA-32-260, and PA-32-300 airplanes. This AD was prompted by reports of corrosion found in an area of the main wing spar not easily accessible for inspection. This AD requires inspecting the left and right main wing spars for corrosion, and, if corrosion is found, taking all necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
Airworthiness Concern Sheet (ACS) for certain Piper aircraft: Model / Series: J-5A, J-5B, J-5C, J-5D, AE-1, HE-1, PA-12, PA-12S, PA-14, PA-16, PA-18, L-21, PA-20, and PA-22 Serial Numbers: All
Recently an accident occurred where the rudder on a PA-12 failed in flight. The airplane was a seaplane equipped with a 160 hp Lycoming O-320 engine. The original tail surfaces had been replaced with PA-18 tail surfaces in accordance with a Supplemental Type Certificate (STC). The broken upper part of the rudder post broke just above the top hinge and the upper part of the rudder folded over the tail brace wires in such a way that rudder control was severely limited and as to effectively create an additional horizontal tail, driving the tail down and the nose up. It was possible for the senior flight instructor to control the airplane in pitch, but required a lot of the available elevator deflection to do so. By dropping the water rudders, some directional control was established and the airplane was able to return to base and land, but with difficulty.
This AD was prompted by a report of damage to the rudder flight control cables and the emergency power supply (EPS) system wiring due to inadequate clearance from the EPS wiring harness. The FAA is issuing this AD to detect, correct, and prevent damaged rudder flight control cables and EPS system wiring. The unsafe condition, if not addressed, could result in electrical arcing between the EPS and the rudder flight control cables with consequent failure of the rudder flight control system. This failure could cause loss of yaw control and lead to loss of control of the airplane during an engine out condition/operation.
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Aspen Avionics, Inc., Evolution Flight Display (EFD) EFD1000 Emergency Backup Display, EFD1000 Multi- Function Display, and EFD1000 Primary Flight Display systems installed on various airplanes. This AD imposes operating restrictions on these display systems by revising the Limitations section of the airplane flight manual (AFM). This AD was prompted by an automatic reset occurring when the display internal monitor detects a potential fault, causing intermittent loss of airspeed, attitude, and altitude information during flight. The FAA is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective August 17, 2020.
The FAA must receive comments on this AD by September 14, 2020.